Unmanned aerial vehicle
AssigneeDefendtex Pty. Ltd.
InventorsTravis Reddy, Damien Cahill
Life of this patent
Estimating the term…
Abstract
An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.
Claims22
1-29. (canceled)
A projectile, comprising:
- a cartridge comprising a propelling charge;
- and
- an elongate unmanned aerial vehicle (UAV) assembly configured to be, in a first configuration, initially attached to the cartridge before the projectile is fired and, in a second configuration, detached from the cartridge and configured to fly free thereof along a first axis after the projectile is fired by the propelling charge, the UAV assembly comprising:
- a body portion, the body portion comprising at least two cutouts whose longest dimensions are parallel to the first axis;
- at least two wing assemblies pivotally attached to the body portion such that each of the at least two wing assemblies is initially being disposed, in a first configuration, within a respective one of the at least two cutouts in the body portion and such that, in a second configuration, at least a portion of each of the at least two wing assemblies is pivoted away from the at least two cutouts to a locked position that is away from the first axis and that is configured for controlled flight;
- an inertial measurement unit (IMU) disposed within the body portion;
- an altimeter disposed within the body portion;
- a microcontroller disposed within he body portion and coupled to the IMU and to the altimeter, the microcontroller being configured to enable the UAV assembly to fly at least partially autonomously when the at least two wing assemblies are in the second configuration;
- a propulsion system coupled to the microcontroller, the propulsion system comprising at least one rotor on each of the at least two wing assemblies, the propulsion system being configured to generate lift when the UAV assembly flies at least partially autonomously;
- and
- a payload coupled to the body portion.
A method, comprising:
- providing a projectile having a cartridge comprising a propelling charge and an elongate unmanned aerial vehicle (UAV) assembly that is configured to be, in a first configuration, initially attached to the cartridge before the projectile is fired and, in a second configuration, detached from the cartridge and configured to fly free thereof after the projectile is fired by the propelling charge;
- causing the propelling charge in the cartridge to fire while the UAV assembly is in the first configuration;
- after the UAV assembly follows a ballistic trajectory for a period of time, transitioning the UAV assembly to the second configuration by extending at least at least two wing assemblies pivotally attached to a body portion of the UAV assembly away from corresponding at least two cutouts in the body portion and generating lift using a propulsion system coupled to each of the at least two wing assemblies;
- controlling, using a microcontroller and sensors within the body portion, at least the propulsion system to enable at least partially autonomous flight of the UAV assembly while in the second configuration;
- and
- delivering a payload disposed at least partially within the UAV assembly to an intended target.
Dependencies are inferred from the claim text.